KR20010108020A - Low drag ducted ram air turbine generator and cooling system - Google Patents

Abstract

A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody/valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.

Description

LOW DRAG DUCTED RAM AIR TURBINE GENERATOR AND COOLING SYSTEM

One type of ram air turbine generator disclosed in the prior art consists of a ram turbine generator with externally mounted blades to draw power from airflow. The blades are usually mounted to the rotatable housing formation of the central light aircraft with the turbine central shaft driven and connected to an electric generator or hydraulic pump or preferably both. Turbine speed control and power output are maintained through a speed control mechanism that changes the pitch of the blades in response to changing flight conditions, thereby maintaining constant power to the blades from airflow. This type of ram air turbine generator is currently the main form used in external conveying electronic pods primarily for emergency power of electrical and / or hydraulic power in military equipment. The unit is stored in the wing or fuselage of the aircraft and deployed into the airflow when there is insufficient power onboard. Recent patents are directed to improvements to this basic technology. U.S. Patent No. 5,249,924 (Brum) relates to a mechanism and a control device for adjusting the pitch of the blades for speed control. US Pat. No. 4,991,796 (Peters et al.) Discloses a drive system between a ram air turbine mounted on a parent aircraft and a power generator. U.S. Patent No. 5,122,036 (Dikes et al.) Discloses an external bladed ram air turbine generator having a mechanism for preventing blades from losing speed and allowing power generation at low speeds, including aircraft landing approach and final landing. have.

In view of the extracted power for power distributed through drag, the process of converting airflow power into mechanical rotational force in an external bladed turbine is relatively efficient at low speeds at an appropriate subsonic speed. However, when the flying speed of the aircraft increases, the efficiency of the process is drastically lowered at a value at which the relative speed between air and the blade becomes the speed of sound. In this regime, the shock waves generated by the blades, together with a sharp increase corresponding to drag, generate high forward pressure on the blades and flow separation above and behind the blades. This can occur at flight speeds in the range of Mach 0.6, depending on blade design and shaft rotation speed. As the flight speed increases to near-sonic speeds to orphan and supersonic flight regimes, the ratio of drag to lift reflects the equivalent increase in drag for the same power extracted from the airflow generated by the blade lift. At least several times may increase depending on the blade profile. These increases in drag can be dangerous for applications to electronic pods mounted on high performance supersonic combat aircraft. Along with the increasing power requirements for electronic systems in external aircraft pods, the disadvantages of these drags for external turbine blade technology have increasing undesirable impacts, speed of reaction, maneuverability and range of travel on aircraft performance. . Moreover, external bladed ram turbine generators do not have the capability to provide cooling directly from the exhaust. In applications involving high speed flight in which portions of the flight profile generate significant aerodynamic heating on the outer shell of the Ford, with additional size and weight disadvantages, additional substantial cooling systems are required for Ford electronics technology. do.

The ducted ram air turbine generator is a ram air turbine of the second type. U. S. Patent 4,267, 775 (sjotun) discloses a ram air turbine generator having a wreath arrangement of inlet ducts for supplying ram air to the inlet of a radial flow turbine and located within the nose portion of the missile. have. The discharge duct directs the discharge flow forward. During the supersonic flight of the missile, the shock waves in front of the missile increase the pressure in front of the discharge, which further pressurizes the flow through the duct and turbine as the missile accelerates, thus limiting the maximum speed of the turbine. However, drag reduction is not a goal and is not provided. The drag is increased for the power extracted by the set reaction force from the complete reversal of the inlet air stream and the resistance to the exhaust flow from the approaching air stream. Direct cooling capability is not provided.

U. S. Patent 4,477, 039 (Boulton et al.) Discloses a vented cowl variable shape inlet for an aircraft. A variable air vent inside the air inlet cowl with a slidable door allows for the discharge of air flow, for example to start the high shrinkage inlet by ram injection and to be positioned to control the air flow to the engine during flight. Can be. The system is used in supersonic aircraft air guidance systems connected with air driven auxiliary power equipment. The system controls the air flow supply for air driven power equipment that requires speed and power control. However, the basic goal provided, which has the shape of the leading edge of the door that diverts flow out through the vent and includes air induction and subsequent aeration, does not provide reduced drag.

US Patent No. 5,505,587, entitled "Ram Air Turbine Generating Apparatus," which is a prior invention of the inventor of the invention, is a power from purely aerodynamic and spring-actuated mechanical internal control elements. A duct ram air turbine is disclosed in which predetermined measurements of output and speed control are obtained. However, the duct ram air turbine of the present invention has the result that the speed and power changes increase by 30% above or below the nominal design value throughout the range of supersonic flight speeds from below normal sonic speed. In many flight applications, the final power supplied to an electronic system typically requires tight tolerances of power and speed within the 5% range. Therefore, the use of the preceding invention may involve additional power regulation systems with the drawback of increased size and weight. The prior invention has a bypass characteristic in which a portion of the air flow is received, bypassed and discharged before being introduced into the thybin. As in Bolton et al., The introduction, bypass and evacuation processes of air flow represent a drawback to drag due to thrust exchange.

The present invention has been devised and modified to carry it out by recognizing the present invention is limited to the spirit of the invention and the spirit to be described hereinafter.

The present invention relates to a ram air turbine device, and more particularly to a duct type ram air turbine generator.

1 is an external perspective view of a ram air turbine generator showing a first embodiment of the present invention;

FIG. 2 is a perspective view of the ram air turbine generator shown in FIG. 1, partially cut away and partially cut away; FIG.

FIG. 3 shows the ram air turbine generation shown in FIG. 1 showing the relative position of the air flow streamline and the relative position of the basic internal components with the diffusely movable center body in the tail wing position and the nozzle control door in the fully open position for flight status design; Half cutaway section of the device.

4 is a perspective view of the ram air turbine generator shown in FIG. 1, showing a portion of the air flow control cross section and an exploded air flow control mechanism;

5A is an enlarged perspective view of a control mechanism positioned in combination with a nozzle and a control door for flight state design of the ram air turbine generator shown in FIG. 1;

FIG. 5B is an enlarged perspective view of a control mechanism positioned in combination with a nozzle and a control door for designing an upper flight state of the ram air turbine generator shown in FIG. 1; FIG.

FIG. 6 is a cross-sectional view taken along line 6-6 of FIG. 3 showing the mating member from the center body / valve tube allowing the center body / valve to slide relative to the longitudinal axis beam and the sliding mechanism in the longitudinal axis beam.

FIG. 6A is an enlarged partial cross sectional view of the sliding member and the axial slot ensuring the central position of the valve tube with respect to the central flow guide member; FIG.

FIG. 7 illustrates the relative position of the primary internal components and the movable central body / valve partially advancing forward with the air stream streamlined and the partially closed nozzle control door for subsonic speeds for higher flight design; Half longitudinal cross section similar to.

8 illustrates the relative position of the shock waves and internal components and airflow streamlines added to the central body nose present with incident impacts at the rear, with the nozzle control door and diffuse tail partially adjacent to the upper supersonic flight state design; Half longitudinal cross section similar to Figure 3 shown.

FIG. 9 is a half similar to FIG. 3 showing the relative position of the primary internal components, with the central body / front valve tube advanced to the maximum forward position providing a streamlined aerodynamic surface for external airflow when no power generation is required. Longitudinal section view.

10 is an operational block diagram of an electronic control system for controlling turbine and generator shaft speeds.

FIG. 11A is a longitudinal half cross-sectional view similar to FIG. 3 showing the relative position of the major internal components for an embodiment of the present invention with cooling capability. FIG.

FIG. 11B is a longitudinal half cross-sectional view similar to FIG. 11A showing the relative position of the internal components for an embodiment of the invention in which cooling capability is provided when cooling is required.

12 is a perspective view of a ram air turbine power generation apparatus in accordance with another embodiment of the present invention, partly cut away and partly shown in cross section.

FIG. 13 is a perspective view of the ram air turbine generator of FIG. 12 with the flow control section and flow mechanism disassembled. FIG.

FIG. 14A is an enlarged fragmentary sectional view of the ram air turbine power generation device of FIG. 12 showing a nozzle control mechanism with nozzle control doors in a fully open position. FIG.

FIG. 14B is an enlarged fragmentary sectional view similar to FIG. 14A showing the nozzle control mechanism with nozzle control doors in the maximum flow restriction position; FIG.

Figure 15A is a cross sectional view taken along line 15-15 when the nozzle control door is in its fully open position.

Figure 15B is a cross sectional view taken along line 15-15 when the nozzle control door is in its maximum flow restriction position;

Figure 16 is an enlarged, partial cross-sectional view of the nozzle first and second control doors in the fully open position showing a flanged bushing that secures the primary and second control doors to each other.

The ram air turbine of the present invention is designed to reduce drag in the step of extracting kinetic energy from steam and converting it to hydraulic and / or electrical power during the full range of intended flight operations. The operating flight regime intended for the present invention is controlled to subsonic speed at high speed via ultrasound. Under conditions, when power generation is required, the aerodynamic central body is advanced forward to the inlet, which completely blocks the air inlet flow while directing the small drag front to steam, leading to the appearance of the device during non-operational mode. Minimized drag is also minimized. In addition to the power generation capability, the present invention has the ability to provide a cooling air flow to the generator and, if desired, other external electronics using exhaust air from the cooled turbine in the stage of operation in the turbine.

According to the present invention, a ram air turbine generator includes a generally cylindrical outer streamlined structure having an air inlet at the tip and an external exhaust port proximate to the trailing end. The outer streamlined structure is mounted to a main structure consisting of a plurality of axially located rings of the front portion of the streamlined structure and longitudinal spars which are in turn attached to the structure bulkhead of the rear portion of the streamlined structure. The axially movable central body / cylindrical valve tube structure is coaxial with, and located radially adjacent to the inner surface of the axial spar and ring, the main structure and the streamlined structure that are front of the bulkhead structure. An aerodynamic forward nose acts as a centroid at the air inlet. The front nose has a maximum diameter smaller than the rear cylindrical valve tube. The trailing portion of the front nose is attached to the trailing cylindrical valve by vanes of aerodynamic shape over the increased radius.

The core / valve tube is slidable with respect to the streamlined structure and the main structure on the axial sliding mechanism on the inner surface of the longitudinal spar of the main structure. The coaxially mounted cylindrical center flow guide has a streamlined structure and an outer surface radially inwardly spaced from the main structure with the front portion slidably receiving the trailing surface of the center body of the center body / valve tube. The center / valve tube front nose forms the center of the annular variable area air inlet. Air flows through the annular space between the outer surface of the front nose and the inner surface of the streamlined structure into the annular opening of the annular channel formed between the aerodynamic vanes, and then the central flow with the inner surface of the plurality of nozzle control doors. It flows into the annular variable area nozzle formed between the outer surface of the guide.

The center / valve tube assembly is movable between the first maximum aft position (position 1), in which case the center nose end is arranged in line axially with the front of the inlet to direct the maximum inlet area to the vapor. The nozzle control mechanism attached to the valve tube positions the nozzle control door at the maximum opening condition. In this position, the maximum airflow is at the variable zone inlet and nozzle passage and is allowed to pass through the stator and turbine wheels, in which part of the kinematic energy of the steam is extracted and discharged to the outside environment through the exhaust deflector and streamlined external exhaust port. It is allowed to be. The turbine generates a power source by driving an electrically coupled generator.

In the second forward position (position 2), when the maximum generator power output is desired, the nose is advanced forward of the inlet face so that the maximum air inlet region is provided in the annular region between the center body and the inner fairing surface. . The nozzle control mechanism brings the nozzle control unit to the maximum extent.

In response to the signal from the turbine speed sensor, the electronic controller activates an electro-mechanical or electro-hydraulic manipulator to move the center / front valve tube. The center / front valve tube is moved to position 2 when flight conditions and generator loads speed the turbine to a given tolerance. The center / front valve tube is moved to position 1 to keep the turbine wheel and generator speed within a predetermined speed range as flight conditions and generator loads lower the turbine speed to within a predetermined tolerance.

Thus, in the full extraction mode, under varying flight conditions by changing air density and flight speed, only sufficient airflow and sufficient kinetic energy are accepted into the turbine through the variable region diffuser and through the variable region nozzle to provide a constant Maintained close to hydrodynamic power. As a result, the turbine and generator speeds are maintained at the desired values. Variable-area nozzles, operating in conjunction with variable-area inlets, adjust variables within the airflow velocity for the stator and turbine, allowing the turbine to effectively extract energy from the airflow at a subsonic speed that is appropriate for subsonic speeds. A combination that accepts only a certain airflow and effectively extracts energy through a planned range of flight maneuvers minimizes drag through the range of maneuvering flight speeds. During a portion of the vehicle, when the power requirement falls below normal operating levels or is completely lost, the center / valve tube is advanced partially or fully forward towards the third or closed position and further reduces or completely closes the inlet airflow. The nozzle is further sealed to provide a clean aerodynamic front that further reduces drag in the reduced or lost power operating mode.

When cooling performance is required for the generator and / or additional electronic system, cooling performance is provided in another embodiment of the present invention. The work of the shaft, carried out by airflow through the turbine, is converted to electrical power by the generator, resulting in exhaust air having an internal energy or temperature lower than the total recovery temperature at the inlet. This cooled exhaust air is discharged directly to the outside environment through the exhaust duct when no cooling effect is required. In an embodiment of the invention providing cooling, a bypass valve is provided in the exhaust duct for cooling regulation. When cooling is required, the bypass valve shuts off airflow to the outside and directs the cooled turbine exhaust to the heat exchanger through the cooling duct downstream of the bypass valve. In order to minimize back pressure that reduces turbine efficiency, the cooling duct is provided with a low density cooling fin that forms the cooling side of the air-air or liquid-air heat exchanger. The other side of the heat exchanger receives heat radiated by the device and cooled through an air or liquid circulation loop.

Advantageous applications of the present invention include the use of electronic pods outside the aircraft during moderate flight at high subsonic speeds through supersonic speeds. It will benefit from ranges from increased aircraft speed and / or reduced drag while extracting power from airflow and in non-operating modes. The air turbine of the present invention results in a smaller maximum outer diameter than current outer blade systems for some level of extracted power. The ram air turbine of the present invention can be used outside the aircraft reservoir or pod for reserve or emergency power to be supplied to the aircraft as needed. The present invention is applicable to both manned and unmanned aerial vehicles. Where cooling capability is desired or desired, embodiments of the present invention having cooling capability provide advantages in size and weight to current systems requiring separate cooling systems when an external blade ram air turbine is used for power generation.

In applications where military radar signatures are important, the ram air turbine of the present invention provides a reduced signature compared to current external blade ram air turbine generators. The rotary turbine of the present invention with the appropriate shaping is not exposed to the outside.

Other advantages and advantages of the ram air turbine of the present invention will become apparent in connection with the following figures. The foregoing description and the following detailed description are exemplary and explanatory and the invention is not so limited. The accompanying drawings show various embodiments of the invention, with or without cooling capability.

First, the overall configuration of a ram air turbine power generation apparatus according to a first embodiment of the present invention will be described with reference to FIGS. The device 28 generally has a cylindrical outer streamlined portion extending between the inlet passage or diffuser 32 at the leading end 34 and the trailing end 36 and having a plurality of exhaust ports 40 near the trailing end. 30). The outer streamlined portion 30 has a plurality of axially spaced peripheral rings 50 located in the front section of the device 28, connected by a plurality of longitudinal spars, and the tail of the device 28. It is mounted to the main structure with a plurality of axially spaced bulkheads located in the section. The center / valve tube 57 is mated with the mating axial slide member 60 located within and subsequently mounted to the inner surface of the longitudinal spar 96 as best shown in FIGS. 6 and 6A. The valve tube 57 is slidably supported in an axial slot 97 that includes a linear ball bearing or other suitable sliding mechanism that projects from the outer surface of the valve tube to the axial slot 97.

The center / valve tube 57 includes a nose end 76 having a forward aerodynamic shape that forms a center body in the air inlet passage 32, the trailing end of the nose end 76 being a nose end ( It is attached by radial vanes 78 having a plurality of aerodynamic shapes to a cylindrical valve tube 56 having a diameter larger than the trailing portion of 76. The cylindrical central flow guide member 42 is coaxial with the valve tube 56 and has the same outer diameter as the trailing portion of the nose end 76 and slidably slides the overlapping trailing portion of the nose end 76 in its inner bore. Accept. This configuration, together with the axial slot 97 and the sliding member 60, allows the center / valve tube 57 with respect to the central flow guide member 42 during the axial movement of the center / valve with respect to the outer streamlined portion 30. Ensure center positioning.

Including the tongue 76 positioned at the maximum aft position (first position), the front end is aligned in line with the tip 34 of the fairing 30 and the maximum air flow is in the inlet or sparger 32. Circular cross section, an annular variable region nozzle 68 defined between the inner surface of the valve tube 56 and the outer surface of the central flow guide member 42, the central flow guide member 42 immediately downstream of the variable region nozzle 68. Penetrates through a plurality of stator vanes 80 and turbine wheels 62 enclosed on an outer surface 44 of the shell, and is rotated outwardly by an exhaust flow deflector 90, after which an internal exhaust port. It is discharged to the peripheral area which penetrates the back of the 40 and the external exhaust port 40.

A plurality of nozzle control door members 55 are positioned midway between the valve tube 56 and the central flow guide member 42 and are fully between the first and second positions when maximum power is required and when the power is reduced. It is operable to control the spent area of the nozzle 68 in response to the movement of the valve tube 56 between the second and third positions where a stationary output is desired. Embodiments of the present invention using either a DC generator (AC) or an AC generator can be configured to maintain a constant turbine or generator speed while reducing a generator field voltage and current that maintains a constant generator output voltage at a reduced load. By automatically positioning the valve tube 56 between the third positions, it is possible to provide reduced power when the electrical load is reduced below the maximum required power.

The nozzle control member 55 is pivotally mounted on the side wall 82 of the nozzle 68 for moving between the retracted and spaced surrounding circumference, and actually contacts the inner surface of the valve tube 56. Control door 70, and an extended position extending into annular nozzle 68 facing central flow guide member 42.

The control door 70 is a plurality of dual nozzle door control cams 115 mounted on the inner surface of the valve tube 56 and a cam mounted on the side wall of the control door 70 opposite the pivot point 120 of the door. The follower 116 mechanism is movable between the retracted and extended positions. By this mechanism and the joint mechanism, each control door 70 is retracted when the valve tube 56 is in the first and extended positions and when in the second position, which will be described in more detail below. Or in an open position.

3 shows the relative position of the air flow field streamlined and internal portion corresponding to the first position, including the inlet and the nozzle in the maximum open position called design flight conditions. Design flight conditions correspond to flight conditions that result from a cube of density and velocity equal to the fluid power per unit area effective in the air stream. This condition will be precisely indicated within the minimum orientation velocity for the altitude curve where maximum power is required. Two common points on the design condition curve are Mach 0.8 at 11100 m and Mach 0.45 at sea level. If the flight speed is above the design conditions at any altitude, the excess fluid power is effective in the air flow, and the system automatically adjusts the effective spreader inlet area and nozzle consumption area, with minimal drag, the turbine to be described in more detail below. And maintain the design of the generator speed and power.

Referring again to FIG. 3, when air enters and flows through an inlet diffuser 32, the extending flow region is defined by the air flow as the kinetic energy partially recovers at increased internal energy and pressure. Causes a decrease. This process continues as the air flow continues to decrease while flowing through the annular channel 48 extending between the inner wall of the fairing 30 and the outer wall of the central guide tube 42. Next, the air flow enters a plurality of variable region nozzle passages 68 formed between the center / valve tube 57 and the center flow guide 42. The flow is accelerated again in the nozzle passage 68 as the flow area is reduced again.

The control unit comprising the nozzle 68, the control door 70 and the nozzle door control member 55 is best shown in FIG. 4, in which the door 70 and the adjacent cam 115 are disassembled for clarity. . The dual track nozzle door control cam 115 with the cam track active surface 125 facing in the inner radial direction is attached to the inner surface of the valve tube 56 removed from this area for clarity. Each dual track nozzle door control cam 115 is located in a space provided between two adjacent nozzle side walls 82. Each pair of nozzle side walls 82 forming the variable region nozzle passage 68 are parallel to each other and attached to a central flow guide. They extend within a small distance of the inner surface of the trailing cylindrical valve tube 56 of the center / valve tube 57.

In Fig. 4 and in an enlarged perspective view, Fig. 5a, the relative position of the door and the control device with respect to the position 1 of the center / valve tube 57 with the door fully open is shown. The actuation surface of the nozzle door control cam 115 is in contact with the door cam follower 116, the contact force provided by the torsion spring 124 and the outwardly acting internal aerodynamics on the cam follower shaft 118. Is applied to. When activated by the nozzle door control cam, the door cam driven shaft 118 extends through a slot 117 outside of the nozzle side wall 82 to accommodate its movement. They are connected to one end of the torsion spring 124 mounted outside the nozzle side wall 82. The cam driven shaft 118 is in turn connected to the side of the nozzle control door 70 extending centrally along the door length through the bearing 122, the door being provided near the top of the side wall 82 of the nozzle 120. The front side is pivotably mounted on the back side).

5b shows the relative position of the door and control device with respect to position 2, i.e. the minimum nozzle area for maximum power generation at a maximum above the design flight conditions. The nozzle door control cam 115 attached to the rear end of the removed valve tube 56 for clarity moved forward with the forward movement of the valve tube 56. The door operates against the cam follower 115 attached to the side of the door 70 and pivots downward by moving against the internal aerodynamic force in the nozzle 68 and the upward force of the torsion spring 124.

The cross-sectional view of FIG. 7 shows the above-described design flight conditions where the power available during the air flow is greater than the design power requirement and the relative position of the air flow flow diagram and the interior portion of the subsonic flight. That is, the nozzle is shown in detail in FIG. 4 in particular. The minimum area of nozzle exhaust is designed to meet the range of complete flight operation requirements in aircraft applications. For example, the design state is Mach = 0.80 (776 ft / sec) at an altitude of 37,000 ft. If the aircraft has sea level velocity characteristics equal to 776 ft / sec (Mach = 0.69) at sea level, as a result, the air density and available hydrodynamic power per unit area are more than four times greater, and the ram air of the present invention The turbine arrangement is designed to reduce the inlet zone and the nozzle zone to at least one quarter of the maximum zone. If the flight speed increases to Mach = 1.6 or twice the design speed, hydrodynamic power is proportional to the cube of the speed and an area reduced to 1 / 8th is required. Typically, all combinations of altitude and corresponding maximum speeds of potential aircraft applications are described to measure the maximum nozzle area reduction.

The contour of the nozzle control door cam 115 to allow maximum nozzle opening in position 1 has a geometric contour in which each position is defined from position 1 towards position 2, at which point the door is closed to the maximum power operating range, The ratio of the total exhaust area of the nozzle to the diffuser of the inlet area is kept constant. Referring again to FIG. 3, a turbine having a plurality of stator 81 radial spar 86 formations extending from the inner radius of the stator 81 to the stator and surrounding the turbine wheel 62 and the stator 81. The central flow guide member 42 of the casing is supported at the rear end by the partition wall 84. The stator and turbine encasing ring 86 are, in turn, attached to the longitudinal spar 96 of the main structure. In the embodiment as shown, the leading edges respectively adjacent to the pair of nozzle sidewalls 82 surrounding the mechanism associated with the cam are aerodynamically elongated leading edges 105 to minimize drag as shown in FIG. Has a front nose with The nozzle control door 70 is spaced between the nozzle side wall 82 and a seal (not shown) on the edge of the control door that mates with the nozzle side wall to minimize leakage.

Again in FIG. 3, the post-emission position of the plurality of annular nozzles of the main internal portion under design conditions, the air flow then flows from the turbine axis to the most efficiently designed flight speed range or flight speed and turbine / generator design speed. And in particular through a plurality of fixed stator blades 80 which rotate in the direction of rotation of the turbine wheel 62 at an optimum angle from the turbine axis for turbine design. In a typical stator blade 80, the blades and turbine / generator rotational speeds of the turbine wheel 62 are designed so that the aircraft provides the most efficiency most of the time, e.g., under conditions of approximately Mach = 0.80 and 37,000 ft. .

For flight conditions of this design, the property of reducing the nozzle area in proportion to the air inlet area maintains the ratio between the air flow rate and the blade inlet turbine close to the flight speed ratio. The use of purely impact turbine blades rotating at constant turbine and generator shaft speeds is most efficient in the region of rotor air outlet speed / turbine inlet speed of 25% or more in design state. Thus, good turbine efficiency can be achieved in instances where the flight speed of Mach + 25% or a flight speed between Mach = 0.60 and Mach = 1.00 or greater than 37,000 feet in height. At water level Mach = 0.5 is 20% greater than the speed of sound at the designed height. The high turbine efficiency remains close to the speed of sound through the supersonic region as shown and described in FIG. During sonic and supersonic flight, conical shock waves 150 are attached to the nose portion of the central body and the flow is deflected outward in the central flow region of the downstream stream Mach number less than the free stream Mach number. The flow then enters through an inlet stationary shockwave 155 at the inlet or in front of the inlet, enters through the diffuser and initially slowly descends and then accelerates into the nozzle passage 68. The nozzle exhaust area is adjusted by being equal to the fixed ratio of the diffuser inlet area for all positions and is provided in a fixed or convergent shape at sonic or supersonic flight speeds, whereby the exhaust is blocked so that the exhaust passes through the sonic region and the supersonic flight region The minimum Mach to pass is limited to 1.0. This ensures that the minimum turbine inlet speed is limited to a minimum no more than 25% greater than the turbine inlet speed under the Mach = 8.0 design, ensuring high turbine efficiency outside of sonic and supersonic flight conditions.

In some applications, high power output and high efficiency are desirable in a wider minimum operating area, that is, from low height to supersonic 37,000 feet for low speed with Mach = 0.40 at water surface. Considering vibrating at the speed of sound at local air temperature, the surface-flying Mach = 0.40 condition is Mach = 0.40 for Mach 1.00 to 970 feet / sec at supersonic at 37,000 feet at standard blade temperatures at both altitudes. Indicates the air speed. In order to impart rotor exhaust tilt angle to the turbine shaft, turbine efficiency is achieved by operating the turbine blades at a speed with a fixed ratio of rotor exhaust speed speed. Thus, by selecting the midpoint of speed, 716 feet / second for the design point, the low and high speed operating points are 35% or more or less from a given point. By using pure impact turbine blades, the reduction in turbine efficiency is over 20%, exceeding this wide speed range. By using a turbine blade design with the same reaction capacity, the reduction efficiency through the wide air velocity region is limited to virtually low values. The reaction blade turbine acts as a nozzle to recover a portion of the air stream kinetic energy by accelerating the flow in the channel between the blades being reduced in the area along the flow path. Pure impact blades of all accelerations that occur before entering the channel of the rotor act like nozzles. The air stream enters and exits the turbine flow channel at the same speed by force varying in the flow direction acting on the moving blade and generated by the moment change, dispersing the force on the blade and performing the operation and Perform the generating power. In order to perform the turbine reaction performance in the case of the high efficiency null fluctuations in accordance with the variation of the embodiment of the present invention, the inlet flow is diffused in a large amount in the diffuser so that a part of the flow acceleration occurs in the blade passage. More overall pressure recovery is allowed by allowing the turbine to operate at higher speeds to achieve this advantage. The configuration of the rotor and turbine combination to achieve the desired performance beyond the available inlet pressure range is a well formed configuration.

After extracting a portion of the fluid power energy from the air stream flow through the turbine, the flow is pivoted outward to flow through the trailing outlet port 40 inside the outside air stream by the trailing flow deflector 90 at low turbulence. . The exhaust is cooled by a turbine expansion process. A portion of the cooled exhaust is oriented through the generator cooling duct 94 and either indirectly cools the generator through conduction or is enclosed within the rear end with a final cooling air discharge port (not shown) as needed. (Not shown), either directly using blast cooling or received by a protrusion cavity through the pod's turbine.

The centrifugal / front valve tube 57 is adapted to move the actuator shaft 104 by a conventional linear electromechanical electrohydraulic actuator 101 located inside the centroid flow guide 42 as shown in FIGS. 3 and 7. Driven forward and backward through. The actuator is fixed on the trailing end at the center in partition 84 in a U-shaped hook-shaped mount. The front end is attached to the actuator shaft 104 by a mount in the form of a U-shaped hook. Movement of actuator 101 is actuated by electronic speed controller 108 in response to turbine / generator speed sensor 107 mounted to turbine / generator shaft 160. Fig. 10 shows an operational schematic diagram of the electronic controller for this embodiment.

Referring to Figure 10, the electromagnetic speed sensor consists of a rotating slot disk 110, the center of which is mounted to the turbine and generator shaft 160. Light emitting diodes 120 and photosensitive transistors 122, called speed sensors, are mounted in brackets 112 with slot disks 110 positioned midway between the diodes and transistors. As the slot disk 110 is rotated, the light beam to the phototransistor is interrupted in generating a series of electron pulses as the phototransistor is turned on and off. The frequency to the voltage converter 133 (standard converter using standard integrated circuit technology) converts a series of pulses into a DC output voltage B that is proportional to the frequency of the pulses. Digitally programmed voltage reference source 132 is comprised of a DC voltage source and a digitally controlled potentiometer. The voltage reference output A of the source 132 corresponds to the desired turbine / generator speed. Switch-operated mode controller 134 is arranged to generate a pulse of two phases at a constant frequency, the pulse width being measured by the difference between the reference voltage A and the frequency at the voltage converter output voltage B. The pulse widths of the outputs A and B of the switched mode controller 134 are inversely proportional. The outputs A and B of the switch mode controller 134 are connected to power amplifiers 136 of two phases of standard technology used to increase the power level of the pulse to the level required to drive the DC motor in the linear actuator. If the frequency is the same for the reference voltage A and the voltage converter output voltage B, the pulse widths of the A and B outputs of the controller 134 in the switched mode are canceled, so that the pure field EMF is applied to the actuator motor 101. And no rotational torque. When the pulse width output A is larger than the frequency converter output B, that is, when the reference voltage A is larger than the frequency converter output B, the rotation speed of the turbine generator is larger than the design speed by the set tolerance. It is small and thereby moves rearward toward position 1 through the ball screw mechanism, the center / valve tube 57, opening the air inlet and nozzle to maintain the turbine / generator within the desired speed range. In the opposite condition, i.e., when the frequency converter output B is larger, the motor is turned in the opposite direction, moving the centroid / valve tube 57 towards position 2, inlet and nozzle to reduce the speed. Seal it. In a preferred embodiment, a ball screw or electrohydraulic mechanism is selected as the actuator 101 for higher reliability.

The generator 58 is located as shown in FIGS. 1, 2, 3, 4, 5, 6, 7, 8, and 9 and penetrates through the interior bore of the blemish bulkhead 88. It is mounted to the blemish bulkhead 88 with the extended shaft 160. The shaft 160 is attached to the shaft connector 130 to accommodate any misalignment between the turbine and generator shafts. The shaft 60 then passes through the hub of the slotted plate 110 and passes through the turbine wheel hub attached to the turbine wheel. And the distal end of the shaft 60 in front of the turbine 62 passes through the front bearing located in the axial center hole of the blemish bulkhead 84 of the central flow guide member 42.

11A and 11B show a first alternate embodiment of the invention in which the cooling capacity of the invention is used. When a cooling effect is needed, for example in the case of an electronic system powered by a ram air turbine, exhaust air from the turbine can be directed through the heat exchanger. When no cooling effect is required, the cooled turbine exhaust air can be transported directly to outside as shown in FIG. 11A. A conventional thermostat mounted on a device to be cooled when a cooling effect is needed and detecting its temperature closes the bypass exhaust valve 140 as shown in FIG. 11B to allow the cooled turbine exhaust air to cool down the cooling duct ( The conventional actuator 142 is started to forcibly pass 144. An array of low density cooling fins is located in the cooling duct at maximum permitted intervals to maintain low turbine back pressure and high turbine efficiency. The high velocity air flow through the duct ensures high heat transfer rates for each cooling fin and the cold side of the heat exchanger. Heat to be cooled from the equipment is removed from the equipment and circulates through the hot side of the heat exchanger using conventional air or liquid circulation methods.

A second embodiment of the nozzle and nozzle control mechanism is shown in Figs. 12, 13, 14A, 14B, 15A, and 15B. This embodiment uses an annular nozzle 272 that includes an intervening panel. It works by uniformly contracting the periphery of the central flow guide 42 to limit the flow through the space between the annular nozzle 272 and the central flow guide 42. First, with respect to Figures 12, 14A and 14B, a number of intervening nozzle control panels 270 and 271 are connected to their respective front and bleed ends by bushings 275 flanged to their respective ends. One flange of each bushing 275 is fastened to the radially inner surface of the radially inner first panel 270. The axis of the bushing projects outwardly through the slotted hole in the second panel 271 with the flange of the other bushing on the radially outer surface of the second panel 271. The flanged bushing 275 allows the first panel and the second panel to maintain a set distance to each other while the first panel and thus the second panel are opened and closed by the mechanism described below.

An inclined slotted linkage 215 is attached to each first panel along the centerline of the outer surface of the panel. The front distal end of each slotted interlock is pivotally mounted to the partition of the panel mounted on the structure 280 extending radially inwardly by the pin hole 220 and the annular panel mounted on the ring 290. 14A shows the first panel 270 in the maximum open position. The cam follower with the plate 217 attached to the inner surface of the partition valve tube 57 pivots the cam follower 216 which in turn is coupled to the slotted hole 230 in the slotted linkage 215. To be installed.

As the septum valve tube 57 is advanced relative to the position of FIG. 14A, the cam type maintains a fixed radial position for all axial positions by the inclination of the slotted holes 230 in the slotted linkage. The eastern portion 216 is subjected to internal aerodynamic forces, such as the slotted linkage 215 and attached first panel 270 rotating clockwise relative to the pin hole 220 and the air flow deflected downward. To respond.

14B shows the relative position of the nozzle control component for the maximum closed position of the nozzle. During forward movement of the valve tube 57, the valve tube slides over the outer surface of the annular panel mounting ring 290, with a sealing means (not shown) located in the groove of the annular mounting ring 290. The annular mounting ring 290 is attached to the central flow guide 42 by a plurality of aerodynamic radial spars, as shown in FIGS. 15A and 15B. This embodiment of the present invention provides for less flow interruption to the stator and turbine than the split nozzle embodiment described above. The movement of the valve tube 57 is controlled by an electronic controller and actuator 101 as in the embodiment described above.

The inclined slot interlock 215 profile, which allows for maximum nozzle opening at position 1, allows the inserted panel of annular nozzle 272 to have maximum total power for each of the front positions of position 1 towards position 2; It has a geometrical contour to define that the ratio of the discharge area of the annular nozzle to the inlet area of the diffuser at the point of closing to the operating range remains constant.

While the preferred embodiments of the present invention have been disclosed in detail, it will be appreciated that various modifications may be made to the described embodiments without departing from the scope of the invention as set forth in the specification and appended claims. Will be understood by the skilled person.

Claims (16)

In a ram air turbine device, A generally cylindrical outer fairing having a front end and a rear end and provided with an air inlet passage at the front end and provided with a plurality of external exhaust ports proximate the rear end; A support structure radially located proximate to an inner surface of the outer fairing supported by the support structure, the support structure comprising a plurality of axial spars; A central flow guide positioned coaxially within the support structure and supported by and spaced apart from the support structure; A valve coaxially positioned midway between the support structure and a central flow guide to a radial proximal portion to the main support structure, the valve having a nose end of an aerodynamic shape and axially movable relative to the outer extension With the tube, A plurality of openings behind the nose end of the valve tube to enable flow of air from the air inlet passage through an annular passage formed between the inner surface of the valve tube and the outer surface of the central flow guide; A turbine wheel having vanes, Stator means for guiding air flow to the turbine vanes; In the annular passageway between the outer surface of the center flow guide and the inner surface of the movable valve tube which is secured to the central flow guide and extends outwardly proximate to the inner surface of the movable valve tube, the air inlet of the outer fairing At least one nozzle extending axially from a position proximal to the rear end to a position proximate to the stator vanes, The valve tube has a shape nose at the valve tube end parallel to the front end of the fairing front, through the air inlet and at least one nozzle and stator vane and turbine vane, and through the fairing external discharge port to the surrounding area. A first position that provides a maximum flow area to the air stream of the air inlet that allows maximum air flow, and the valve tube is advanced such that the shape nose end of the valve tube limits the air inlet area and thereby at least one The second position will result in reduced air flow through the nozzle and stator vanes and through the fairing external outlet port to the surrounding area, and the valve tube will be advanced to the maximum forward position so that the valve tube's shape nose will completely close the air inlet. In contact with the inner surface of the fairing air inlet The ram air turbine device, characterized in that movable between three positions. 2. The central flow guide as set forth in claim 1, wherein the valve is in the middle of a central flow guide operative to control the flow of air through the nozzle in response to movement of the valve tube between the first, second and third positions. Ram air turbine apparatus characterized in that it further comprises a nozzle control unit. The method of claim 2, wherein the nozzle control unit, Positioned between and pivotally supported between the pair of parallel nozzle sidewalls for movement between the retracted positions substantially in contact with the inner surface of the valve tube and the extended positions projecting radially inward toward the nozzle. A plurality of peripherally spaced control doors, A cam follower mounted to each of the control doors at a position spaced apart from the pivotal support of the door, And a slot in the nozzle sidewall that forms a cam such that a cam follower in the slot moves the control door between a fully retracted position and a fully extended position. 4. The ram air turbine device of claim 3 wherein the nozzle control maintains a fixed ratio of the total discharge area of the nozzles to the area of the air inlet passage. The method of claim 2, wherein the nozzle control unit, A number of alternating fits pivotally supported on the panel mounting ring and positioned therebetween for movement between the retracted position substantially in contact with the inner surface of the valve tube and the extended position radially inwardly projecting towards the nozzle First and second nozzle control panels, A cam slot mounted to each of the first nozzle control panels at a position spaced from the pivotal support of the first nozzle control panel on the panel mounting ring; The cam follower mounted on the valve tube is urged to move the first nozzle control panel and the second nozzle control panel fitted in the middle between the fully retracted position and the fully extended position by the movement of the cam follower in the cam slot. Ram air turbine device comprising a. 6. The ram air turbine device of claim 5 wherein the nozzle control maintains a fixed ratio of the total discharge area of the nozzles to the area of the air inlet passage. An external fairing having an air supply passage at the tip and tapered radially inward toward the tip and having a generally cylindrical shape and extending to the rear end and having a plurality of external exhaust ports near the rear end, A main structural means disposed radially close to the inner surface of the outer fairing to extend the length of the fairing means, the main structural means having a plurality of straight axial airfoils mounted with the fairing means and extending the length of the outer fairing; , A central flow guide means coaxially mounted to the support structure, the outer surface being isolated from the rescue means; A rear large valve disposed in a middle portion of the central flow guide means coaxial with the main rescue means and at a position radially close to the main rescue means, having a pneumatic airfoil extending in diameter to extend; A central body / valve tube means comprising an aerodynamically shaped nose having a rear tubular portion connected to the tube portion, A plurality of openings supporting in a position isolated from the nose end of the central member / valve tube rear end allowing air to enter through an annular passage formed between the opening in the nose and the valve tube inner surface and the central flow guide means; , Turbine wheels coupled to generators or hydraulic pumps or both, Stator means for directing air flow to the turbine blades; Formed in the radial range within the perimeter range between the side wall means of the nozzle set in parallel in the annular passageway between the outer wall of the central flow guide means and the inner wall of the movable valve tube and mounted to the central flow guide means A plate extending outward in a range close to the inner wall of the movable valve tube means and the nozzle side wall means, the position proximate to the stator in the axial direction from an axial position near the rear end of the main inlet in the outer pay ring A plurality of nozzle means extending backwards to The shaped nose of the valve tube is aligned with the leading end of the fairing front end to provide a maximum area flow area for the airflow within the main inlet of the outer fairing, the maximum airflow through the main inlet, the shaping of the valve tube. A first position allowing flow to the peripheral region through the plurality of inlet holes, through the annular nozzle, through the stator, through the turbine, through an exhaust deflector and the fairing exhaust port in the finished nose; The valve tube is advanced such that the shaped nose end of the valve tube restricts the main air supply area through the main inlet, through the plurality of the inlet holes in the shaped nose of the valve tube, through the annular nozzle Via the stator, through the turbine, through the exhaust deflector and the pairing port A second position causing the airflow towards the area to be reduced, and a third position wherein the valve tube is advanced toward the maximum forward position such that the shaped nose of the valve tube contacts the inner surface of the fairing main air inlet so that the inlet is completely closed A valve tube means movable between, Speed sensor means for detecting the speed of the turbine wheel; Responsive to the speed sensor means when the speed of the turbine wheel is returned to a predetermined speed by reducing the air flow to the turbine through the main inlet flow zone and the main air inlet by exceeding a predetermined value. Moving the valve tube forward toward the second position and moving the valve tube back toward the first position in response to the speed sensor when the speed of the turbine wheel is lower than a predetermined value, thereby moving the inlet flow region and the main airflow inlet. And an actuator configured to restore airflow to the turbine through the nozzle and to return the turbine wheel at a predetermined speed, and to move the valve tube forward to the third position when the power output is stopped to close the inlet flow region. A ram air turbine generator, comprising speed control means. 8. A method according to claim 7, wherein it is intermediate between the valve tube means and the central flow guide means and operable to control air flow through the nozzle in response to movement of the valve tube means between first, second and third positions. And a nozzle control means. A plurality of circumferentially positioned and pivotally mounted between each of the nozzle side vanes to move between a generally continuous retracted position and an extended position radially inwardly projected into the annular nozzle With control doors spaced apart by A plurality of cam followers each rotatably mounted to a shaft extending adjacent to and extending circumferentially outwardly from each of the side walls of the control door opposite the door mounting pivot; A slot in the side wall of the nozzle side vane in which movement of the shaft of the cam follower is received in the nozzle side vane when the nozzle control door moves between a full retracted position and an extended position; A plurality of twin cams radially inwardly extending into a plurality of channels, each axially mounted to an inner surface of the valve tube and positioned between outer surfaces joining the nozzle vanes; A plurality of torsional springs each attached at one end to an outer surface about the nozzle vane and engaged at the other end to a cam follower shaft, Outward force acts on the cam follower to maintain contact between each cam follower and cam for all positions of the cam and cam follower, and each side of the twin cam is adjacent from each surface of the adjacent control doors. Simultaneously engage with a cam follower, each of the control doors remain in the retracted position when the control tube is in the first position, and each of the control doors in the extended position when the valve tube means is in the second position. RAM air turbine generator, characterized in that maintained. 9. The apparatus of claim 8, comprising track means for radial positioning and for enabling axial sliding movement of the valve tube relative to the main structure, The track means consists of a plurality of grooves in the radially inner surface of the longitudinal spars of the main structure, And wherein each of the grooves receives a mating protrusion member of the valve tube that slides with low friction in the grooves. The method of claim 8, wherein the central flow guide means has an axial bore therein, And the valve tube means rear end is slidably received in the axial bore of the central flow guide means. 8. A valve according to claim 7, wherein said valve tube means comprises an aerodynamically formed front portion forming said shaped nose end, A plurality of air inlet channels are circumferentially spaced about the nose ends of the molded nose and installed rearward therefrom, A cylindrical body is connected to the shaped nose by an aerodynamically formed spar and extends rearward to an axial position very close to the front of the stator, wherein a plurality of the aerodynamically formed spars have a small diameter of the nose shaped rearwardly. A ram air turbine generator, characterized in that connected to the large diameter valve tube. 13. A turbine according to claim 12, comprising a turbine having a turbine shaft rotatably mounted at the rear end of the rear plate member of the central flow guide at the front end and at the plate mounted to the main structure at the rear end. Ram air turbine generator. 14. The turbine of claim 13, further comprising: a front bearing on said center flow guide means for rotatably mounting said one end of said turbine shaft and said turbine rear of a main structure partition for rotatably mounting said other end of said turbine shaft. And a rear bearing on the plate. 15. The apparatus of claim 14, further comprising a generator mounted to a rear side of an axially located generator mounting plate mounted to a main structure, and a shaft coupler for driving coupling the rear shaft of the turbine to a generator shaft, And the generator mounting plate has a bearing for rotatably mounting the shaft of the generator, wherein a portion of the generator shaft extends forwardly through the bearing. 8. The actuator of claim 7 wherein the actuator and speed control means comprise an electronic speed control circuit and a reduced speed corresponding to the required turbine speed and rearward toward the first position when an increased speed corresponding to the required turbine speed is desired. And an actuator controlled by said speed control circuit to position said valve tube forward toward a third position when turbine speed is desired.